Abstract
The Induced drag of a wing with optimum lift distributions is studied, which lies on a diameter of a closed wind tunnel of circular cross section. Exact expressions of the spanwise lift distribution and the induced drag are obtained from the Trefftz plane flow field. When the ratio b/d of wing span to tunnel diameter increases, the lift distribution changes gradually from elliptic to uniform ones, and the induced drag also gradually decreases until it becomes zero. An alternative solution based on the method of matched asymptotic expansions confirms the exact theory to be valid. Throughout this paper the flow is assumed inviscid and incompressible, whereas the viscous effect are briefly descirbed.
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